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AUTOMATIC GAS TURBINE MATCHING SCHEME ADAPTATION FOR ROBUST GPA DIAGNOSTICS
Mälardalen University, School of Business, Society and Engineering, Future Energy Center.ORCID iD: 0000-0003-0739-8448
Mälardalen University, School of Business, Society and Engineering, Future Energy Center.ORCID iD: 0000-0001-6101-2863
Mälardalen University, School of Business, Society and Engineering, Future Energy Center.ORCID iD: 0000-0002-8466-356X
2019 (English)In: Proceedings of the ASME Turbo ExpoVolume 6, 2019, 2019, Vol. 6Conference paper, Published paper (Refereed)
Abstract [en]

When performing gas turbine diagnostics using Gas Path Analysis (GPA), a convenient way of extracting the degradations is by feeding the measured data from a gas turbine to a well-tuned gas turbine performance code, which in turn calculates the deltas on the chosen health parameters matching the measured inputs. For this, a set of measured parameters must be matched with suitable health parameters, such as deltas on compressor and turbine efficiency and flow capacity.

In aero engines, the number of sensors are in general limited due to cost and weight constraints and only the necessary sensors for safe engine operation are available. Some important sensors may have redundancy in case of a sensor loss but it is far from certain that this applies to all sensors available.

If a sensor malfunctions by giving false or no values, the functions using the sensor will be negatively affected in some way causing them to either synthesize a fictive measurement, changing operating scheme, going into a degraded operating mode or shutting down parts or the whole process. If an onboard diagnostic algorithm fails due to sensor faults it will lead to a decrease in flight safety, thus there is a need for a robust system.

This paper presents a strategy for automatic modifications of the gas turbine diagnostic matching scheme when sensors malfunction to ensure a robust function. When a sensor fault is detected and classified as malfunctioning, the gas turbine matching scheme is modified according to predefined rules. If possible, a redundant measurement replaces the faulty measurement. If not, the matching scheme will be modified by determining if any health parameters cannot be derived by the functional set of measurements and remove the least valuable health parameter while maintaining a working matching scheme for the remaining health parameters.

Place, publisher, year, edition, pages
2019. Vol. 6
Keywords [en]
Gas Path Analysis, Diagnostics, Gas Turbine
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:mdh:diva-45866DOI: 10.1115/GT2019-91018Scopus ID: 2-s2.0-85075527511OAI: oai:DiVA.org:mdh-45866DiVA, id: diva2:1366380
Conference
ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, GT 2019; Phoenix; United States; 17 June 2019 through 21 June 2019; Code 154121
Projects
DIAGNOSIS
Funder
Knowledge Foundation, 20160133Available from: 2019-10-29 Created: 2019-10-29 Last updated: 2019-12-02Bibliographically approved

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Stenfelt, MikaelZaccaria, ValentinaKyprianidis, Konstantinos
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